Safe aircraft ammunition container

ABSTRACT

Aircraft ammunition is loaded nose-down in an ejectable container that is attached to the bottom of the aircraft external to primary aircraft structure, to minimize peril in the event of explosion of the ammunition.

United States Patent [191 Seibel SAFE AIRCRAFT AMIVIUNITION CONTAINER[75] Inventor: Charles M. Seibel, Hurst, Tex.

[73] Assignee: Textron, Inc., Providence, R.1.

[22] Filed: Feb. 28, 1974 [21] Appl. No.: 446,701

[52] US. Cl 89/34; 89/37.5 R; 244/137 R [51] Int. Cl. B64D l/04 [58]Field of Search 89/l.5 F, 34, 37.5 R, 37.5 C

[56] References Cited UNITED STATES PATENTS 6/1921 Schneider 89/37.5 R

3/1936 Helwig 89/37.5 R 11/1941 Martin 89/37.5 R

Primary ExaminerStephen C. Bentley Attorney, Agent, or FirmRichards,Harris & Medlock ABSIRACT Aircraft ammunition is loaded nose-down in anejectable container that is attached to the bottom of the aircraftexternal to prirnary aircraft structure, to minimize eril in the eventof explosion of the ammuni- Hon.

7 Claims, 4 Drawing Figures US. Patent Oct. 14, 1975 Sheet1of2 3,911,787

U.S. Patent Oct. 14, 1975 Sheet 2 0f 2 Fig.

SAFE AIRCRAFT AMMUNITION CONTAINER FIELD OF THE INVENTION This inventionrelates to storage of ammunition on board an aircraft, and moreparticularly, to an ammunition container located on an aircraft externalto primary aircraft structure with orientation of the ammunition withinan ejectable container so as to ensure aircraft safety.

PRIOR ART Ammunition containers on board an aircraft are typicallyhoused within the aircraft fuselage or wing, or within gun pods firmlyattached to the aircraft. The feeding mechanism draws either beltedammunition from a standard linked ammunition cannister or delinkedammunition from a drum magazine.

Ammunition linked in belts has characteristically been used with weaponshaving low rates of fire. The ammunition is fed to the gun by a feedmechanism which draws belted ammunition from the container, extracts theammunition from the belt links, feeds the ammunition to the gun, andejects the links and spent cases. The linear movements of the guncomponents in recoil and counter-recoil are transformed mechanically toprovide the drive means for the feed mechanism. Electric, hydraulic, orpneumatic devices may provide alternate external power to drive the feedmechanism.

With weapons having high rates of fire, such as those utilizing theVulcan principle, linkless feed systems are employed because of theproblems associated with link and spent ammunition disposal. Thelinkless feed system contains either a single or twin ammunitionconveyor belt within flexible chuting. With a single belt the spentcases are ejected overboard, but in many installations a return conveyorfor spent cartridge cases is povided. A central rotor in the form of ahelical archimidean screw moves the round from the drum into theconveyor in a multi-stage operation. The system may be driven by a ramair turbine, or from gun gas bled from the barrels. If linked ammunitionis used it is fed through the gun via a delinking feeder typicallydriven by an electric or hydraulic motor.

Each of these weapon systems enclose the ammunition container within anaircraft member. Further, the ammunition is stored in the container andconveyed to the gun with the projectile pointed at either the crew oressential components of the flight system. During periods of emergencywhich arise from such contingencies as a direct hit or an impendingcrash, the crew must rely primarily on blast barriers to survive anyensuing explosion of the ammunition container.

SUMMARY OF THE INVENTION The present invention is directed to aircraftammunition storage to provide for rapid ejection of the ammunition intimes of emergency, and to minimize peril to the aircraft and crew whilethe container remains in aircraft storage.

More particularly, the ammunition is stored nosedown in the container,directed away from the aircraft and crew. The ammunition container isnested in a cavity in the underside of the aircraft behind the gunturret, with the bottom of the container forming the lower contour ofthe aircraft.

Pyrotechnic units secure the ammunition storage unit to the aircraft andare adapted to sever and force. the container down and away from thehelicopter.

In a still further aspect, the forward portion of the system isconnected to the storage portion by means of break-away fasteners sothat upon ejection the forward portion remains in place.

DESCRIPTION OF THE DRAWINGS For a more complete understanding of thepresent invention and for further objects and advantages thereof,references may now be had to the following description taken inconjunction with the accompanying drawings in which:

FIG. 1 is a perspective view of a helicopter with part of the fuselagebroken away to illustrate an ammunition container coupled to a feedmechanism supplying ammunition to a weapon.

FIG. 2 is a sectional view looking down from the top of a helicopteronto an integrated weapon system including an ammunition container.

FIG. 3 is a perspective view of an ammunition container with a portionof the outer housing broken away showing nose-down orientation ofammunition.

FIG. 4 is a sectional view of a helicopter feeding mechanism.

DESCRIPTION OF A PREFERRED EMBODIMENT Referring to FIGS. 1 and 2, a flatstorage and linkless feed system supplies ammunition to weapon 11. Thestorage system incorporates a unique ammunition storage container 2which is a rectangular box. An ammunition feed chute 4 and a returnchute 6 house conveyor elements which transport ammunition to a weaponfeeder. Chute 4 is connected to one corner of container 2 and to aflexible-shaft drive booster 7 forward of the container. Another sealedfixed chute 8 is connected from booster 7 and extends forward to areceptacle to which a flexible chute 9 is attached. Chute 9 routes theammunition into the weapon feeder in a turret 10. The empty conveyorleaves the feeder in a flexible chute which attaches to the other cornerof container 2 in the same manner as the feed chute. Chute 6 routes theconveyor back to a comer of the container 2. Chutes 6 and 9 are sealedand serve to vent the gun gases above the turret.

A drive shaft 5a is shown connected between the container 2 and booster7. Drive shaft 5b is connected from booster 7 to the receptacle of chute8.

Two beams 14a and 14b contain structure for supporting gear boxes andindex mechanisms for required stoker and exit sprockets.

A solid barrier 3 provides blast protection for the aircraft and crew.

To eject container 2, ejection forces are produced by four pyrotechnicthrusters l which secure container 2 to helicopter 12. When ejection isinitiated, the thrusters 1 sever container 2 and force it down and awayfrom aircraft 12. The forward portion of the feed mechanism is connectedto container 2 by means of breakaway fasteners 13. When the container isejected, the forward portion of the feed mechanism remains in place.

In FIG. 3 container 2 is ejected from aircraft 12 with stored ammunition15 in a nose-down orientation. Thus, the ammunition is always pointedaway from the helicopter and crew when stored on board an aircraft.

In FIG. 4, container 2 is located in a cavity behind the gun turret inthe underside of aircraft 12. The bottom of the container forms thelower contour of aircraft 12 in the area of the cavity. The containerhas blow-out cover 16 over its entire surface below the bulk of theammunition. Should an explosion occur in the storage area, the blow-outcover offers the path of least resistance and vents the majority of theconcussion or debris down and away from the aircraft l2 and its crew,control system, and other flight essential components.

In accordance with the present invention, there is provided arectangular aircraft ammunition container within which ammunition isstored nose-down away from aircraft and crew. Pyrotechnic thrusterssecure the container in a cavity in the under side of the aircraft,while break-away fasteners couple the container to the on board feedmechanism. The base of the container is a blow-out cover forming thelower contour of the aircraft in the area of the cavity.

In the event of impending danger, the container may be ejected by firingsupport thrusters. If the container explodes while secured to theaircraft, the blow-out cover vents the majority of the concussion anddebris away from the aircraft.

Having described the invention in connection with certain specificembodiments thereof, it is to be understood that further modificationsmay now suggest themselves to those skilled in the art and it isintended to cover such modifications as fall within the scope of theappended claims.

What is claimed is:

1. An airborne ammunition container for an aircraft, comprising:

a. a housing container to accommodate ammunition pieces;

b. said housing container connected to said aircraft external to theprimary aircraft structure;

0. a blowout cover on the bottom of said ammunition container whereby anexplosion in the container can be vented down through the cover;

d. means for storing ammunition pieces within said housing containersuch that the trajectory of said ammunition pieces when detonated withinsaid container is away from said aircraft; and

e. means to eject said housing container from said aircraft.

2. The combination as set forth in claim 1, wherein said ejecting meanscomprise a plurality of pyrotechnic thrusters.

3. The combination as set forth in claim 2, wherein said thrusters arefour in number.

4. The combination of claim 1 additionally comprising a solid barrierpositioned over said ammunition container whereby the aircraft and creware provided with blast protection thereby.

5. In an airborne weapon system in which a feed mechanism transportsammunition to a weapon, the combination which comprises:

a. an aircraft fuselage with an ammunition container nested in anunderside open cavity and connected to said aircraft external of primaryaircraft structure;

b. means for storing ammunition in said container with the projectilespointing downward away from said fuselage and means comprising a blowoutcover on the bottom of the ammunition container;

c. a plurality of breakaway fasteners to connect said container to saidfeed mechanism; and

d. a plurality of pyrotechnic thrusters to disconnect said containerfrom said aircraft.

6. The combination as set forth in claim 5, wherein said thrusters arefour in number.

7. The combination as set forth in claim 5 additionally comprising asolid barrier positioned over said ammunition container whereby theaircraft and crew are provided with blast protection thereby.

1. An airborne ammunition container for an aircraft, comprising: a. ahousing container to accommodate ammunition pieces; b. said housingcontainer connected to said aircraft external to the primary aircraftstructure; c. a blowout cover on the bottom of said ammunition containerwhereby an explosion in the container can be vented down through thecover; d. means for storing ammunition pieces within said housingcontainer such that the trajectory of said ammunition pieces whendetonated within said container is away from said aircraft; and e. meansto eject said housing container from said aircraft.
 2. The combinationas set forth in claim 1, wherein said ejecting means comprise aplurality of pyrotechnic thrusters.
 3. The combination as set forth inclaim 2, wherein said thrusters are four in number.
 4. The combinationof claim 1 additionally comprising a solid barrier positioned over saidammunition container whereby the aircraft and crew are provided withblast protection thereby.
 5. In an airborne weapon system in which afeed mechanism transports ammunition to a weapon, the combination whichcomprises: a. an aircraft fuselage with an ammunition container nestedin an underside open cavity and connected to said aircraft external ofprimary aircraft structure; b. means for storing ammunition in saidcontainer with the projectiles pointing downward away from said fuselageand means comprising a blowout cover on the bottom of the ammunitioncontainer; c. a plurality of breakaway fasteners to connect saidcontainer to said feed mechanism; and d. a plurality of pyrotechnicthrusters to disconnect said container from said aircraft.
 6. Thecombination as set forth in claim 5, wherein said thrusters are four innumber.
 7. The combination as set forth in claim 5 additionallycomprising a solid barrier positioned over said ammunition containerwhereby the aircraft and crew are provided with blast protectionthereby.